Machine Casting of High Temperature Alloys for Turbine Engine Components

1977 ◽  
Author(s):  
L. F. Schulmeister ◽  
J. D. Hostetler ◽  
C. C. Law
Keyword(s):  
High Temperature ◽  
Turbine Engine ◽  
High Temperature Alloys ◽  
Engine Components

TIMETAL 829

Alloy Digest ◽  
2001 ◽  
Vol 50 (8) ◽  
Keyword(s):  
Fracture Toughness ◽  
Titanium Alloy ◽  
High Temperature ◽  
High Strength ◽  
Heat Treating ◽  
High Temperature Alloy ◽  
Turbine Engine ◽  
Major Application ◽  
Alpha Titanium ◽  
Engine Components

Abstract TIMETAL 829 is a Ti-5.5Al-3.5Sn-3Zr-1Nb-0.25Mo-0.3Si near-alpha titanium alloy that is weldable and has high strength and is a creep resistant high temperature alloy. The major application is as gas turbine engine components. This datasheet provides information on composition, physical properties, elasticity, and tensile properties as well as fracture toughness, creep, and fatigue. It also includes information on forming and heat treating. Filing Code: TI-118. Producer or source: Timet.

High temperature telemetry systems for in situ monitoring of gas turbine engine components

2009 ◽  
Author(s):  
Brian Keyes ◽  
Jeffrey Brogan ◽  
Christopher Gouldstone ◽  
Robert Greenlaw ◽  
Jie Yang ◽  
...  
Keyword(s):  
High Temperature ◽  
Gas Turbine ◽  
Gas Turbine Engine ◽  
In Situ Monitoring ◽  
Turbine Engine ◽  
Temperature Telemetry ◽  
Engine Components

HARVEY HA-7146

Alloy Digest ◽  
1964 ◽  
Vol 13 (4) ◽  
Keyword(s):  
High Temperature ◽  
Heat Treating ◽  
Age Hardening ◽  
High Temperature Strength ◽  
Turbine Engine ◽  
Temperature Performance ◽  
Aluminum Company ◽  
Alpha Beta ◽  
Engine Components ◽  
Hardening Heat Treatment

Abstract Harvey HA-7146 is an alpha-beta type titanium-base bar and forging alloy developed to combine high temperature strength and stability with good forgability. It is recommended for aircraft gas turbine engine components due to its improved stress stability and creep resistance. It responds to an age hardening heat treatment. This datasheet provides information on composition, physical properties, hardness, elasticity, and tensile properties as well as fracture toughness, creep, and fatigue. It also includes information on high temperature performance and corrosion resistance as well as forming, heat treating, machining, joining, and surface treatment. Filing Code: Ti-39. Producer or source: Harvey Aluminum Company.

High-Temperature Surface Measurements of Turbine Engine Components Using Thermographic Phosphors

1997 ◽  
Author(s):  
Sami Alaruri ◽  
Andy Brewington
Keyword(s):  
High Temperature ◽  
Gas Flow ◽  
Single Point ◽  
Temperature Measurements ◽  
Turbine Engine ◽  
Thermographic Phosphors ◽  
Engine Component ◽  
Surface Measurements ◽  
Engine Components ◽  
Temperature Surface

A laser-based system for single point high-temperature measurements of turbine engine component surfaces coated with thermographic phosphors is described. Decay lifetime calibration measurements obtained for Y2O3:Eu over the temperature range ∼530–1000°C are presented. Further, the results obtained from a coupon placed in the outlet gas flow of an atmospheric-combustor are described.

scholarly journals THE FORMATION OF HIGH TEMPERATURE MINERALS FROM AN EVAPORITE-RICH DUST IN GAS TURBINE ENGINE INGESTION TESTS

2021 ◽  
pp. 1-11
Author(s):  
Jacob Elms ◽  
Alison Pawley ◽  
Nicholas Bojdo ◽  
Merren Jones ◽  
Rory J. Clarkson
Keyword(s):  
High Temperature ◽  
Gas Turbine ◽  
Previous Analysis ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Complete Understanding ◽  
Turbine Engine ◽  
Mineral Assemblages ◽  
Mineral Dusts ◽  
Engine Components

Abstract The ingestion of multi-mineral dusts by gas turbine engines during routine operations is a significant problem for engine manufacturers because of the damage caused to engine components and their protective thermal barrier coatings. A complete understanding of the reactions forming these deposits is limited by a lack of knowledge of compositions of ingested dusts and unknown engine conditions. Past engine tests have used standardised test dusts that do not resemble the composition of the background dust in the operating regions. A new evaporite-rich test dust was developed and used in a full engine ingestion test, designed to simulate operation in regions with evaporite-rich geology, such as Doha or Dubai. Analysis of the engine deposits showed that mineral fractionation was present in the cooler, upstream sections of the engine. In the hotter, downstream sections, deposits contained new, high temperature phases formed by reaction of minerals in the test dust. The mineral assemblages in these deposits are similar to those found from previous analysis of service returns. Segregation of anhydrite from other high temperature phases in a deposit sample taken from a High Pressure Turbine blade suggests a relationship between temperature and sulfur content. This study highlights the potential for manipulating deposit chemistry to mitigate the damage caused in the downstream sections of gas turbine engines. The results of this study also suggest that the concentration of ingested dust in the inlet air may not be a significant contributing factor to deposit chemistry.

UNITEMP 41

Alloy Digest ◽  
1981 ◽  
Vol 30 (4) ◽  
Keyword(s):  
Fracture Toughness ◽  
High Temperature ◽  
High Strength ◽  
Heat Treating ◽  
Vacuum Melting ◽  
Jet Engine ◽  
Temperature Performance ◽  
High Temperature Alloys ◽  
Nickel Base ◽  
Engine Components

Abstract UNITEMP 41 is a nickel-base, precipitation-hardenable alloy that retains high strength and finds most use in the temperature range 1200 to 1800 F. It is produced by one or more vacuum melting practices. This alloy is one of the strongest high-temperature alloys that can be formed and welded in sheet form; consequently, it is used widely for jet engine components. Other uses include turbine buckets, turbine wheels, rings and high-temperature fasteners and springs. This datasheet provides information on composition, physical properties, hardness, elasticity, and tensile properties as well as fracture toughness. It also includes information on low and high temperature performance, and corrosion resistance as well as forming, heat treating, machining, joining, and surface treatment. Filing Code: Ni-267. Producer or source: Cyclops Corporation.

scholarly journals The Formation of High Temperature Minerals From an Evaporite-Rich Dust in Gas Turbine Engine Ingestion Tests

2020 ◽  
Author(s):  
Jacob Elms ◽  
Alison Pawley ◽  
Nicholas Bojdo ◽  
Merren Jones ◽  
Rory Clarkson
Keyword(s):  
High Temperature ◽  
Gas Turbine ◽  
Operating Conditions ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Test Bed ◽  
Turbine Engine ◽  
Mineral Assemblages ◽  
Mineral Dusts ◽  
Engine Components

Abstract The ingestion of multi-mineral dusts by gas turbine engines during routine operations is a significant problem for engine manufacturers because of the damage caused to engine components and their protective thermal barrier coatings. A complete understanding of the reactions forming these deposits is limited by a lack of knowledge of compositions of ingested dusts and unknown engine conditions. Test bed engines can be dosed with dusts of known composition under controlled operating conditions, but past engine tests have used standardised test dusts that do not resemble the composition of the background dust in the operating regions. A new evaporiterich test dust was developed and used in a full engine ingestion test, designed to simulate operation in regions with evaporiterich geology, such as Doha or Dubai. Analysis of the engine deposits showed that mineral fractionation was present in the cooler, upstream sections of the engine. In the hotter, downstream sections, deposits contained new, high temperature phases formed by reaction of minerals in the test dust. The mineral assemblages in these deposits are similar to those found from previous analysis of service returns. Segregation of anhydrite from other high temperature phases in a deposit sample taken from a High Pressure Turbine blade suggests a relationship between temperature and sulfur content. This study highlights the potential for manipulating deposit chemistry to mitigate the damage caused in the downstream sections of gas turbine engines. The results of this study also suggest that the concentration of ingested dust in the inlet air may not be a significant contributing factor to deposit chemistry.

Feasibility Study of Intermetallic Composites

1990 ◽  
Vol 194 ◽  
Author(s):  
D. M. Shah ◽  
D. L. Anton ◽  
C. W. Musson
Keyword(s):  
Mechanical Properties ◽  
High Temperature ◽  
Gas Turbine ◽  
Equilibrium Phase ◽  
Physical And Mechanical Properties ◽  
Turbine Engine ◽  
Wide Range ◽  
Phase Compatibility ◽  
Engine Components ◽  
Phase Relationships

AbstractThe feasibility of developing high-temperature intermetallic composites for use as gas turbine engine components is assessed for a wide range of high temperature intermetallic matrices including aluminides, silicides, Laves and Sigma phases along with Al2O3, SiC, TiC, Si3N4 and Y2O3 as well as ductile refractory metals as either reinforcing phases or coatings. Preliminary evaluations of fabricability and observations of matrix/reinforcing phase compatibility are presented and discussed in terms of various factors, including interstitial impurities, equilibrium phase relationships, kinetics, and physical and mechanical properties of both matrix and reinforcing phases.

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